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针对某空间遥感器主承力结构-机身结构进行了设计与分析。首先通过对比分析对机身进行结构选型,然后优选出一种新兴材料作为机身结构材料,即高体分硅铝合金材料,并确定连接方案,然后再通过拓补优化手段对机身结构进行优化,把反射镜组件等负载等效成力偶,进行合理的边界约束,大体上确定基本形式,进而优化出一种薄壁加筋结构,在保证机身动、静态刚度的前提下,提高了材料的轻量化率,并应用计算机仿真手段进行了静、动态及热特性的分析。分析结果证明该方案是合理可行的。
Aiming at the main force structure of a space remote sensor - fuselage structure design and analysis. First of all, through comparative analysis of the structure of the body selection, and then choose a new material as a fuselage structure material, that is, high-volume silicon-aluminum alloy material, and determine the connection scheme, and then through the extension and optimization of the fuselage structure Optimized, the mirror assembly and other loads equivalent to couple, reasonable boundary constraints, generally determine the basic form, and then optimize the thin-walled stiffened structure, to ensure the dynamic and static stiffness of the fuselage under the premise of improving The rate of weight reduction of materials, and the application of computer simulation of static, dynamic and thermal characteristics of the analysis. The result of the analysis proves that the scheme is reasonable and feasible.